Wingle system, method for wingle system and aircraft
By forming the cover plate with the upper and lower blades in the winglet system, the problem of the need to install the cover structure separately after the lower blade is removed, achieving the effect of simplifying maintenance and reducing costs.
Patent Information
- Application Number
- CN202411970922.5
- Authority / Receiving Office
- CN · China
- Patent Type
- Applications(China)
- Current Assignee / Owner
- Priority Date
- 2024-02-16
- Filing Date
- 2024-12-30
- Publication Date
- 2025-08-19
AI Technical Summary
The existing winglet system needs to be installed separately after the lower blade is removed, resulting in time and labor cost problems.
A winglet system is designed in which the cover plate is formed integrally with the upper blade and the lower blade, covering the openings in the transition joint and fixed by fragile fasteners to ensure that the cover plate remains fixed to the upper blade when the lower blade is separated, avoiding the individual installation of the cover structure.
This enables no additional installation of the covering structure after the lower blade is removed, simplifies the maintenance process, reduces time and costs, and ensures the normal flight of the aircraft.
Smart Images
Figure CN120503954A_ABST
Abstract
Description
Technical Field
[0001] Examples of the present disclosure generally relate to winglet systems and methods for an aircraft, such as winglet systems and methods disposed at the end of a wing. Background Art
[0002] Some aircraft include winglets extending from the distal end of the main wing structure. Winglets are configured to reduce drag, for example, by partially recovering wingtip vortex energy. Various winglets are configured to increase the lift generated at the wingtip (by smoothing the airflow across the upper wing near the wingtip) and reduce the drag caused by the lift caused by the wingtip vortex, thereby improving the lift-to-drag ratio.
[0003] Known winglets include an upper blade and a lower blade. The lower blade extends downward relative to the wing tip, thereby reducing ground clearance relative to the wing tip. Consequently, the lower blade may be susceptible to accidental impact, for example, from ground service vehicles at an airport. In such cases, the lower blade can be removed. After a separate and different structure is installed over the opening created by the removal of the lower blade, the aircraft can temporarily fly without the lower blade.
[0004] As can be appreciated, the process of obtaining and installing separate and distinct structures over the openings is time and labor consuming, and can be expensive. Summary of the Invention
[0005] There is a need for improved winglets. Additionally, there is a need for systems and methods for effectively and efficiently compensating for the removal of a winglet's lower blade.
[0006] In light of these needs, certain embodiments of the present disclosure provide a winglet system configured to be secured to the wing of an aircraft. The winglet system includes an upper blade, a lower blade, and a cover plate integrally formed with the upper and lower blades. The cover plate covers an opening within a transition joint between the upper and lower blades. If the lower blade detaches from the winglet system, the cover plate remains coupled to the upper blade.
[0007] In at least one embodiment, the cover plate includes a cover panel disposed within the opening and one or more couplers extending from the cover panel. As an example, the one or more couplers include a first coupler (e.g., a rear or front coupler) and a second coupler (e.g., a front or rear coupler). In at least one embodiment, the one or more couplers include legs separated by a gap.
[0008] In at least one embodiment, the lower blade includes one or more attachment fittings secured to the one or more couplings. As another example, the cover panel includes one or more channels. The one or more attachment fittings extend through the one or more channels. In at least one embodiment, the one or more attachment fittings are secured to the one or more couplings via one or more frangible fasteners.
[0009] In at least one embodiment, the upper blade includes one or more attachment fittings secured to the one or more couplings. As another example, the one or more couplings are secured to the one or more first attachment fittings of the upper blade via one or more first fasteners. The one or more couplings are secured to the one or more second attachment fittings of the lower blade via one or more second fasteners. The one or more first fasteners are different from the one or more second fasteners. In at least one embodiment, the one or more first attachment fittings do not extend to or contact the one or more second attachment fittings.
[0010] In at least one example, at least one fastener secures the one or more couplers to the one or more first attachment fittings of the upper blade and the one or more second attachment fittings of the lower blade. As another example, the one or more retaining fasteners secure the one or more couplers to the one or more first attachment fittings of the upper blade. The one or more retaining fasteners are not connected to the one or more second attachment fittings of the lower blade.
[0011] Certain examples of the present disclosure provide a method for a winglet system configured to be secured to a wing of an aircraft. The method includes integrally forming a cover plate with an upper blade and a lower blade.
[0012] Certain examples of the present disclosure provide an aircraft including a fuselage, wings extending from the fuselage, and a winglet system secured to each wing, as described herein. BRIEF DESCRIPTION OF THE DRAWINGS
[0013] Figure 1 Shown is a perspective front view of an aircraft according to an example of the present disclosure.
[0014] Figure 2 A perspective side view of a winglet system according to an example of the present disclosure is shown.
[0015] Figure 3 A perspective top view of a winglet system at a transition joint is shown according to an example of the present disclosure.
[0016] Figure 4 A cross-sectional view of a coupling according to an example of the present disclosure is shown.
[0017] Figure 5 Shown is a perspective side of a winglet system with the lower blade removed according to an example of the present disclosure.
[0018] Figure 6 A perspective top view of a winglet system at a transition joint is shown according to an example of the present disclosure.
[0019] Figure 7 A top view of a rear coupler of a cover plate according to an example of the present disclosure is shown.
[0020] Figure 8 A top view of a front coupler of a cover plate according to an example of the present disclosure is shown. DETAILED DESCRIPTION
[0021] When read in conjunction with the accompanying drawings, the foregoing overview and the following detailed description of certain embodiments will be better understood. As used herein, elements or steps stated in the singular and preceded by the word "one" or "a kind of" should be understood to not necessarily exclude multiple elements or multiple steps. In addition, reference to "one embodiment" is not intended to be interpreted as excluding the existence of additional embodiments that also incorporate the features described. In addition, unless explicitly stated to the contrary, embodiments that "comprise" or "have" an element or multiple elements with a specific condition may include additional elements that do not have that condition.
[0022] As described herein, embodiments of the present disclosure provide a winglet system comprising an integrated cover plate disposed between an upper blade and a lower blade. The integrated cover plate is not separate or distinct from the winglet system. Rather, the cover plate is integrally formed with the winglet system. The winglet system allows an aircraft to fly without the lower blade and eliminates the need for installing a separate and distinct cover structure. The winglet system incorporates the cover plate and also includes a frangible attachment point for the lower blade.
[0023] Figure 1 A perspective front view of an aircraft 100 according to an example of the present disclosure is shown. Aircraft 100 includes a propulsion system that may include, for example, two engines 112. Alternatively, the propulsion system may include more engines 112 than shown. Engines 112 are carried by wings 116 of aircraft 100. In other examples, engines 112 may be carried by fuselage 118 and / or tail 120. Tail 120 may also support multiple horizontal stabilizers 122 and one vertical stabilizer 124.
[0024] A winglet system 130 is secured to a distal end 131 of each wing 116. Each winglet system 130 includes an upper blade 134 and a lower blade 136. The upper blade 134 extends upwardly above the plane of the upper surface of the wing 116. The lower blade 136 extends downwardly below the plane of the upper surface of the wing 116.
[0025] Figure 1The aircraft 100 shown in FIG. 1 is an example only. The size and shape of the aircraft 100 may vary. Figure 1 Different as shown.
[0026] Figure 2 A perspective side view of a winglet system 130 according to an example of the present disclosure is shown. The winglet system 130 includes an upper blade 134 coupled to a lower blade 136 at a transition joint 138 , which may include an upper cover fairing 139 .
[0027] Figure 3 A perspective top view of the winglet system 130 at a transition joint 138 is shown, according to an example of the present disclosure. Figure 3 The upper cover fairing 139 (not shown) Figure 2 shown).
[0028] The winglet system 130 includes a cover plate 140 that is integrally formed with the winglet system 130. That is, the cover plate 140 is an integral part of the winglet system 130 rather than being separately mounted to the winglet system, such as with the lower blade 136 removed.
[0029] The cover plate 140 includes a cover panel 142 disposed within an opening 143 of the transition joint 138. A first coupler 144 extends inward from an inner surface 145 of the cover panel 142. The first coupler 144 may be a rear coupler. A second coupler 146 also extends inward from the inner surface 145 of the cover panel 142. The second coupler 146 may be a front coupler. Alternatively, the first coupler 144 may be a front coupler, and the second coupler 146 may be a rear coupler. The inner surface 145 is opposite to the outer surface 147. The first coupler 144 and the second coupler 146 are separated by a distance 148. The first coupler 144 and the second coupler 146 each include coupling legs 150 and 152 separated by a gap 154. The cover plate 140 may include fewer or more couplers than shown. For example, the cover plate 140 may include a single coupler. As another example, the cover plate 140 may include three couplers.
[0030] The proximal end 160 of the lower blade 136 is adjacent to (such as abutting) the outer side surface 147 of the cover panel 142. The lower blade 136 includes a plurality of attachment fittings 164 that extend through a channel formed through the cover panel 142. Each attachment fitting 164 extends between the coupling legs 150 and 152 of one of the first coupler 144 and the second coupler 146. One or more fasteners 166 (such as bolts) secure the attachment fitting 164 to the first coupler 144 and the second coupler 146. The fasteners 166 are non-frangible.
[0031] Upper blade 134 also includes a plurality of attachment fittings 170. Each attachment fitting 170 extends between the coupling legs 150 and 152 of one of the first and second couplings 144 and 146. One or more fasteners 172 (e.g., bolts) secure the attachment fittings 170 to the first and second couplings 144 and 146. In at least one embodiment, these fasteners 172 are frangible fasteners (such as frangible bolts) that are configured to break under a predetermined force, allowing lower blade 136 to be separated from winglet system 130. Frangible fasteners are configured to withstand flight loads but break in response to a predetermined excessive load (such as from an impact of a specific magnitude). Fastener 166 is configured to withstand a greater load than fastener 172. In this manner, fastener 166 ensures that cover plate 140 remains secured to winglet system 130 even if frangible fastener 172 breaks, allowing lower blade 136 to be separated from winglet system 130. Alternatively, the fastener 172 may be a removable fastener rather than a frangible fastener.
[0032] As an example, if ground support equipment strikes lower blade 136 with sufficient force, lower blade 136 may need to be removed and repaired. To remove, fasteners 166 may be removed so that lower blade 136 may be removed, but cover plate 140 remains in place.
[0033] Figure 4 A cross-sectional view of a coupler according to an example of the present disclosure is shown. The coupler may be a first coupler 144. A second coupler 146 may be similarly constructed. An attachment fitting 164 extends between the coupling legs 150 and 152 of the coupler at a first end 180, while an attachment fitting 170 extends between the coupling legs 150 and 152 at an opposite second end 182. The attachment fitting 164 does not extend to or contact the attachment fitting 170. In this manner, in at least one example, the fastener 166 securing the coupler to the attachment fitting 164 does not contact the attachment fitting 170. Similarly, the fastener 172 securing the coupler to the attachment fitting 170 does not contact the attachment fitting 164.
[0034] like Figure 4 As shown, one or more couplers (such as first coupler 144 and / or second coupler 146) are secured to one or more attachment fittings 170 of upper blade 134 by one or more fasteners 172. One or more couplers are also secured to one or more attachment fittings 164 of lower blade 136 by one or more fasteners 172 (such as frangible bolts). Fasteners 172 are different from fasteners 166.
[0035] Figure 5 A perspective side view of a winglet system 130 is shown with the lower blade removed, according to an example of the present disclosure. Figures 2 to 5With the lower blade 136 removed, the cover panel 140 remains within the opening 190 of the transition joint 138 of the winglet system 130. The cover panel 142 is configured to conform to the size and shape of the opening 190. As shown, the cover panel 142 is contoured to an airfoil. As described above, the cover panel 142 includes a plurality of channels 192 through which the attachment fittings 164 are configured to pass.
[0036] With the lower blade 136 removed from the winglet system 130, the cover plate 140 formed integrally with the winglet system 130 provides a cover panel 142 that covers the opening 190. Thus, a separate and distinct cover structure need not be separately secured to the winglet system 130.
[0037] Figure 6 A perspective top view of the winglet system 130 at a transition joint 138 is shown, according to an example of the present disclosure. Figure 7 A top view of the second coupler 146 of the cover plate 140 is shown, according to an example of the present disclosure. Figure 8 A top view of the first coupler 144 of the cover plate 140 is shown according to an example of the present disclosure.
[0038] See also Figures 6 to 8 In this example, the attachment fitting 170 of the upper blade 134 includes opposing fins 200 and 202 separated by a gap 204. The attachment fitting 170 extends between the coupling legs 150 and 152. The attachment fitting 164 of the lower blade 136 extends between the fins 200 and 202. Fasteners 206, such as bolts, secure the first coupler 144 and the second coupler 146 to each of the attachment fittings 164 and 170. That is, each fastener 206 is secured to each of the attachment fittings 164 and 170. In at least one example, the fasteners 206 are frangible and are configured to break under a predetermined force, thereby allowing the lower blade 136 to be separated from the winglet system 130.
[0039] One or more retaining fasteners 220, such as bolts, secure one or both of the first coupler 144 and / or the second coupler 146 to the attachment fitting 170. In at least one example, the retaining fasteners 220 are neither connected to nor secured to the attachment fitting 164. The retaining fasteners 220 are configured to ensure that the cover plate 140 remains secured to the upper blade 134 in the event that the lower blade 136 is separated from the winglet system 130, such as when the lower blade 136 is removed for repair or maintenance.
[0040] As shown, the first coupler 144 may include a retaining fastener 220 that provides a secondary connection to the attachment fitting 170 of the upper blade 134. The second coupler 146 may not include the retaining fastener 220. Optionally and / or additionally, the second coupler 146 may include the retaining fastener 220. In at least one example, both the first coupler 144 and the second coupler 146 may include a retaining fastener, such as the retaining fastener 220.
[0041] See also Figures 1 to 8 Embodiments of the present disclosure provide a winglet system 130 having an integrally formed cover panel 140 configured to remain secured to the winglet system 130 when the lower blade 136 is separated from the winglet system 130. When the lower blade 136 is separated from the winglet system 130, the cover panel 140 remains secured to the winglet system 130, such as within the opening 190 of the transition joint 138. Thus, if the lower blade 136 does separate from the winglet system 130, the aircraft 100 can still fly without requiring a separate and distinct cover structure to be installed on the winglet system 130. If the lower blade 136 does separate from the winglet system 130, thereby exposing the cover panel 142 within the opening 190, the exposed channel 192 of the cover panel 142 can be covered with a covering agent, such as quick-catch tape.
[0042] As described herein, the winglet system 130 includes a cover plate 140 that provides an integrated, split blade tip cover. When the winglet system 130 is manufactured, the cover plate 140 is installed and integrally formed with the winglet system 130. If there is a need to remove the lower blade 136, the cover plate 140 is already in place, and the aircraft operator does not need to obtain a separate and distinct covering structure to fly the aircraft. In at least one embodiment, the cover plate 140 is secured to one or more attachment fittings of the lower blade 136 (alone or both) using a plurality of frangible fasteners 206 (such as a plurality of frangible bolts), while also being secured to one or more additional attachment points (such as portions of the attachment fitting 170 of the upper blade 134) using additional fasteners.
[0043] As described herein, see Figures 1 to 8The winglet system 130 is configured to be secured to the wing 116 of the aircraft 100. The winglet system 130 includes an upper blade 134, a lower blade 136, and a cover plate 140 integrally formed with the upper blade 134 and the lower blade 136. That is, the winglet system 130 is manufactured with the cover plate 140 coupled to the upper blade 134 and the lower blade 136. The cover plate 140 is not separately secured to the winglet system 130 after the winglet system 130 is manufactured. The cover plate 140 covers the opening 190 in the transition joint 138 between the upper blade 134 and the lower blade 136. If the lower blade 136 is separated from the winglet system 130, the cover plate 140 remains coupled to the upper blade 134.
[0044] Furthermore, the present disclosure includes implementations according to the following clauses:
[0045] Clause 1. A winglet system configured to be secured to a wing of an aircraft, the winglet system comprising: an upper blade; a lower blade; and a cover plate integrally formed with the upper blade and the lower blade, wherein the cover plate covers an opening in a transition joint between the upper blade and the lower blade, and wherein if the lower blade is detached from the winglet system, the cover plate remains coupled to the upper blade.
[0046] Clause 2. The winglet system of clause 1, wherein the cover comprises: a cover panel disposed within the opening; and one or more couplers extending from the cover panel.
[0047] Clause 3. The winglet system of clause 2, wherein the one or more couplers include: a first coupler; and a second coupler.
[0048] Clause 4. The winglet system of clause 2 or 3, wherein the one or more couplers comprise legs separated by a gap.
[0049] Clause 5. The winglet system of any of clauses 2 to 4, wherein the lower blade includes one or more attachment fittings secured to the one or more couplings.
[0050] Clause 6. The winglet system of clause 5, wherein the cover panel includes one or more channels, and wherein the one or more attachment fittings extend through the one or more channels.
[0051] Clause 7. The winglet system of clause 5 or 6, wherein the one or more attachment fittings are secured to the one or more couplers by one or more frangible fasteners.
[0052] Clause 8. The winglet system of any of clauses 2 to 7, wherein the upper blade includes one or more attachment fittings secured to the one or more couplings.
[0053] Clause 9. A winglet system according to any of clauses 2 to 7, wherein the one or more couplers are secured to the one or more first attachment fittings of the upper blade by one or more first fasteners, wherein the one or more couplers are secured to the one or more second attachment fittings of the lower blade by one or more second fasteners, and wherein the one or more first fasteners are different from the one or more second fasteners.
[0054] Clause 10. The winglet system of clause 9, wherein the one or more first attachment fittings do not extend to or contact the one or more second attachment fittings.
[0055] Clause 11. The winglet system of any of clauses 2 to 9, wherein at least one fastener secures the one or more couplers to the one or more first attachment fittings of the upper blade and the one or more second attachment fittings of the lower blade.
[0056] Clause 12. The winglet system of clause 11, wherein the one or more retaining fasteners secure the one or more couplers to the one or more first attachment fittings of the upper blade, and wherein the one or more retaining fasteners are not connected to the one or more second attachment fittings of the lower blade.
[0057] Clause 13. A method for a winglet system configured to be secured to a wing of an aircraft, the method comprising: integrally forming a cover plate with an upper blade and a lower blade, wherein the cover plate covers an opening in a transition joint between the upper blade and the lower blade, and wherein if the lower blade is separated from the winglet system, the cover plate remains coupled to the upper blade.
[0058] Clause 14. An aircraft comprising: a fuselage; wings extending from the fuselage; and a winglet system secured to each wing, the winglet system comprising: an upper blade; a lower blade; and a cover plate integrally formed with the upper blade and the lower blade, wherein the cover plate covers an opening in a transition joint between the upper blade and the lower blade, and wherein if the lower blade is detached from the winglet system, the cover plate remains coupled to the upper blade.
[0059] Clause 15. The aircraft of clause 14, wherein the cover comprises: a cover panel disposed within the opening; and one or more couplers extending from the cover panel.
[0060] Clause 16. The aircraft of Clause 15, wherein the one or more couplers include: a first coupler; and a second coupler.
[0061] Clause 17. The aircraft of clause 15 or 16, wherein the one or more couplers comprise legs separated by a gap.
[0062] Clause 18. An aircraft according to any of clauses 15 to 17, wherein the lower blade includes one or more first attachment fittings secured to the one or more couplers, wherein the cover panel includes one or more channels, wherein the one or more first attachment fittings extend through the one or more channels, and wherein the one or more first attachment fittings are secured to the one or more couplers by one or more frangible fasteners.
[0063] Clause 19. The aircraft of clause 18, wherein the upper blade includes one or more second attachment fittings secured to the one or more couplings.
[0064] Clause 20. The aircraft of clause 19, wherein the one or more couplers are secured to the one or more second attachment fittings of the upper blade by one or more fasteners.
[0065] As described herein, examples of the present disclosure provide an improved winglet system. Additionally, examples of the present disclosure provide systems and methods for effectively and efficiently compensating for a removed lower blade of a winglet.
[0066] Although various spatial and directional terms (such as top, bottom, lower, middle, lateral, horizontal, vertical, front, etc.) may be used to describe embodiments of the present disclosure, it should be understood that these terms are used only with respect to the orientation shown in the drawings. The orientation may be inverted, rotated, or otherwise changed so that the upper portion is the lower portion, the rear portion may become the front portion and vice versa, the horizontal becomes vertical, etc.
[0067] As used herein, a structure, limitation, or element that is "configured to" perform a task or operation is specifically structurally formed, constructed, or adapted in a manner corresponding to the task or operation. For the sake of clarity and avoidance of doubt, an object that is merely capable of being modified to perform a task or operation is not "configured for" performing a task or operation as used herein.
[0068] It should be understood that the foregoing description is intended to be illustrative and not restrictive. For example, the above-described embodiments (and / or aspects thereof) may be used in combination with each other. Furthermore, many modifications may be made to adapt a particular situation or material to the teachings of the various embodiments of the present disclosure without departing from the scope of the present disclosure. While the dimensions and types of materials described herein are intended to define the parameters of the various embodiments of the present disclosure, these embodiments are by no means limiting and are merely illustrative embodiments. Many other embodiments will be apparent to those skilled in the art upon reviewing the foregoing description. Therefore, reference should be made to the appended claims, along with the full scope of equivalents to which such claims are entitled, to determine the scope of the various embodiments of the present disclosure. In the appended claims and the detailed description herein, the terms "including" and "in which" are used as the plain-English equivalents of the respective terms "comprising" and "wherein." Furthermore, the terms "first," "second," and "third," etc. are used merely as labels and are not intended to impose numerical requirements on their objects. Furthermore, the appended claim limitations are not written in a means-plus-function format and are not intended to be interpreted under 35 U.S.C. § 112(f) unless such claim limitations expressly qualify the phrase "means for..." using a functional description that does not include other structure.
[0069] This written description uses examples to disclose various embodiments of the disclosure, including the best mode, and also to enable any person skilled in the art to practice the various embodiments of the disclosure, including making and using any devices or systems and performing any incorporated methods. The patentable scope of the various embodiments of the disclosure is defined by the claims and may include other examples that occur to those skilled in the art. If an example has structural elements that do not differ from the literal language of the claims, or if an example includes equivalent structural elements that do not differ substantially from the literal language of the claims, such other examples are intended to fall within the scope of the claims.
Claims
1. A winglet system (130) configured to be secured to a wing of an aircraft (100), the winglet system (130) comprising: Upper blade (134); lower blade (136); as well as A cover plate (140) is formed integrally with the upper blade (134) and the lower blade (136), wherein the cover plate (140) covers an opening (143, 190) in a transition joint (138) between the upper blade (134) and the lower blade (136), and wherein if the lower blade (136) is separated from the winglet system (130), the cover plate (140) remains coupled to the upper blade (134).
2. The winglet system (130) of claim 1, wherein: The cover plate (140) includes: a cover panel (142) disposed within the opening (143, 190); and One or more couplers extending from the cover panel (142).
3. The winglet system (130) of claim 2, wherein: The one or more couplers include: A first coupler (144); and A second coupling (146).
4. The winglet system (130) of claim 2, wherein: The one or more couplers include legs separated by a gap (154).
5. The winglet system (130) of claim 2, wherein: The lower blade (136) includes one or more attachment fittings (170) secured to the one or more couplings.
6. The winglet system (130) of claim 5, wherein: The cover panel (142) includes one or more channels, and wherein the one or more attachment fittings (170) extend through the one or more channels.
7. The winglet system (130) of claim 5, wherein: The one or more attachment fittings (170) are secured to the one or more couplers by one or more frangible fasteners (172).
8. The winglet system (130) of claim 2, wherein: The upper blade (134) includes one or more attachment fittings (170) secured to the one or more couplings.
9. The winglet system (130) of claim 2, wherein: The one or more couplers are secured to one or more first attachment fittings (170) of the upper blade (134) by one or more first fasteners (172), wherein the one or more couplers are secured to one or more second attachment fittings (170) of the lower blade (136) by one or more second fasteners (172), and wherein the one or more first fasteners (172) are different from the one or more second fasteners (172).
10. The winglet system (130) of claim 9, wherein: The one or more first attachment fittings (170) do not extend to or contact the one or more second attachment fittings (170).
11. The winglet system (130) of claim 2, wherein: At least one fastener secures the one or more couplers to the one or more first attachment fittings (170) of the upper blade (134) and the one or more second attachment fittings (170) of the lower blade (136).
12. The winglet system (130) of claim 11, wherein: One or more retaining fasteners (172) secure the one or more couplers to the one or more first attachment fittings (170) of the upper blade (134), and wherein the one or more retaining fasteners (172) are not connected to the one or more second attachment fittings (170) of the lower blade (136).
13. A method for a winglet system (130) configured to be secured to a wing of an aircraft (100), the method comprising: A cover plate (140) is integrally formed with an upper blade (134) and a lower blade (136), wherein the cover plate (140) covers an opening (143, 190) within a transition joint (138) between the upper blade (134) and the lower blade (136), and wherein if the lower blade (136) is separated from the winglet system (130), the cover plate (140) remains coupled to the upper blade (134).
14. An aircraft (100), comprising: fuselage (118); Wings (116) extending from the fuselage (118); as well as A winglet system (130) secured to each of the wings (116), the winglet system (130) comprising: Upper blade (134); lower blade (136); and A cover plate (140) is formed integrally with the upper blade (134) and the lower blade (136), wherein the cover plate (140) covers an opening (143, 190) in a transition joint (138) between the upper blade (134) and the lower blade (136), and wherein if the lower blade (136) is separated from the winglet system (130), the cover plate (140) remains coupled to the upper blade (134).
15. The aircraft (100) according to claim 14, wherein The cover plate (140) comprises: a cover panel (142) disposed within the opening (143, 190); and One or more couplers extending from the cover panel (142).
16. The aircraft (100) according to claim 15, wherein: The one or more couplers include: A first coupler (144); and A second coupling (146).
17. The aircraft (100) of claim 15, wherein: The one or more couplers include legs separated by a gap (154).
18. The aircraft (100) of claim 15, wherein: The lower blade (136) includes one or more first attachment fittings (170) secured to the one or more couplers, wherein the cover panel (142) includes one or more channels, wherein the one or more first attachment fittings (170) extend through the one or more channels, and wherein the one or more first attachment fittings (170) are secured to the one or more couplers by one or more frangible fasteners (172).
19. The aircraft (100) according to claim 18, wherein: The upper blade (134) includes one or more second attachment fittings (170) secured to the one or more couplings.
20. The aircraft (100) of claim 19, wherein: The one or more couplers are secured to the one or more second attachment fittings (170) of the upper blade (134) by one or more fasteners (172).